Internet Archive Search: (collection:ufnaca OR mediatype:ufnaca) AND -mediatype:collection AND firstTitle:P

Search Results

Results: 1 through 15 of 15 (0.002 secs)
You searched for: (collection:ufnaca OR mediatype:ufnaca) AND -mediatype:collection AND firstTitle:P

	Performance of basic XJ79-GE-1 turbojet engine and its components - United States.: National Advisory Committee for Aeronautics http://uf.catalog.fcla.edu/uf.jsp?st=UF003852967&ix=nu&I=0&V=D&pm=1 Keywords: Airplanes--Turbojet engines Downloads: 62
	Plane problem of the flapping wing - United States.: National Advisory Committee for Aeronautics http://uf.catalog.fcla.edu/uf.jsp?st=UF003780265&ix=nu&I=0&V=D&pm=1 Keywords: Aerodynamics; Airplanes--Wings--Testing Downloads: 37
	Prediction of motions of an airplane resulting from abrupt movement of lateral or directional controls - Langley Aeronautical Laboratory http://uf.catalog.fcla.edu/uf.jsp?st=UF003613074&ix=nu&I=0&V=D&pm=1 Keywords: Ailerons; Yawing (Aerodynamics Downloads: 32
	Preliminary flight research on an all-movable horizontal tail as a longitudinal control for flight at high mach numbers - Langley Aeronautical Laboratory http://uf.catalog.fcla.edu/uf.jsp?st=UF003614162&ix=nu&I=0&V=D&pm=1 Keywords: Mach number; Compressibility; Fighter planes; Aerodynamics--Research Downloads: 46
	Preliminary investigation of supersonic diffusers - Langley Aeronautical Laboratory http://uf.catalog.fcla.edu/uf.jsp?st=UF003638287&ix=nu&I=0&V=D&pm=1 Keywords: Diffusers; Aerodynamics, Supersonic Downloads: 57
	Preliminary report on a study of separated flows in supersonic and subsonic streams - Ames Research Center http://uf.catalog.fcla.edu/uf.jsp?st=UF003853244&ix=nu&I=0&V=D&pm=1 Keywords: Laminar flow; Turbulence; Transition flow; Aerodynamics Downloads: 46
	Preliminary survey of possible cooling methods for hypersonic aircraft - Lewis Research Center http://uf.catalog.fcla.edu/uf.jsp?st=UF003810781&ix=nu&I=0&V=D&pm=1 Keywords: Hypersonic planes; Airplanes--Motors--Cooling; Aerodynamics--Research Downloads: 34
	Present state of development in nonsteady motion of a lifting surface : = Lo stato attuale delle ricerche sul moto instazionario di una superficie portante - United States.: National Advisory Committee for Aeronautics http://uf.catalog.fcla.edu/uf.jsp?st=UF003689766&ix=nu&I=0&V=D&pm=1 Keywords: Aeronautics; Aerofoils Downloads: 46
	Pressure distribution and pressure drag for a hemispherical nose at Mach numbers 2.05, 2.54, and 2.04 - Langley Aeronautical Laboratory http://uf.catalog.fcla.edu/uf.jsp?st=UF003809150&ix=nu&I=0&V=D&pm=1 Keywords: Aerodynamics--Research; Drag (Aerodynamics Downloads: 58
	Pressure distributions on three bodies of revolution to determine the effect of Reynolds number up to and including the transonic speed range Keywords: Body of revolution; Aerodynamics, Transonic Downloads: 42
	Problem of slip flow in aerodynamics - United States.: National Advisory Committee for Aeronautics http://uf.catalog.fcla.edu/uf.jsp?st=UF003853242&ix=nu&I=0&V=D&pm=1 Keywords: Aerodynamics; Air flow Downloads: 78
	Problem of torsion in prismatic members of circular segmental cross section - United States.: National Advisory Committee for Aeronautics http://uf.catalog.fcla.edu/uf.jsp?st=UF003875298&ix=nu&I=0&V=D&pm=1 Keywords: Aerodynamics; Torsion Downloads: 69
	Procedure for calculating turbine blade temperatures and comparison of calculated with observed values for two stationary air-cooled blades - Lewis Research Center http://uf.catalog.fcla.edu/uf.jsp?st=UF003810529&ix=nu&I=0&V=D&pm=1 Keywords: Aircraft gas-turbines--Blades; Aerodynamics--Research Downloads: 46
	Profile-drag coefficients of conventional and low-drag airfoils as obtained in flight - Langley Aeronautical Laboratory http://uf.catalog.fcla.edu/uf.jsp?st=UF003605308&ix=nu&I=0&V=D&pm=1 Keywords: Aerofoils; Aeronautics--Research Downloads: 43
	Propellers in yaw - Langley Aeronautical Laboratory http://uf.catalog.fcla.edu/uf.jsp?st=UF003805565&ix=nu&I=0&V=D&pm=1 Keywords: Propellers, Aerial; Yawing (Aerodynamics; Aeronautics--Research Downloads: 55